81 FR 26103 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 84 (May 2, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 84 (May 2, 2016)
| Page Range | 26103-26106 | |
| FR Document | 2016-09235 |
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)] [Rules and Regulations] [Pages 26103-26106] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-09235] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3970; Directorate Identifier 2015-SW-006-AD; Amendment 39-18497; AD 2016-08-20] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding airworthiness directive (AD) 2014-12-51 for Airbus Helicopters (previously Eurocopter France) Model EC130B4 and [[Page 26104]] EC130T2 helicopters. AD 2014-12-51 required repetitively inspecting the tailboom to Fenestron junction frame (junction frame) for a crack. This new AD retains the requirements of AD 2014-12-51, changes the applicability from helicopters with certain hours time-in-service (TIS) to junction frames with certain hours TIS, and adds a compliance time for sling cycles to the junction frame inspection interval. The actions of this AD are intended to detect a crack and to prevent failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter. DATES: This AD is effective June 6, 2016. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of June 6, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641- 3775; or at http://www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. It is also on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3970. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3970; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion On September 25, 2015, at 80 FR 57742, the Federal Register published our notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2014-12-51, Amendment 39-17921 (79 FR 45335, August 5, 2014), and add a new AD. AD 2014-12-51 applied to Airbus Helicopters Model EC130B4 and EC130T2 helicopters with 690 or more hours TIS and required, within 10 hours TIS, dye-penetrant inspecting certain areas of the junction frame for a crack. AD 2014-12-51 also required, at intervals not exceeding 25 hours TIS, either repeating the dye- penetrant inspection or performing a borescope inspection of certain areas of the junction frame for a crack. If there was a crack, AD 2014- 12-51 required replacing the junction frame. AD 2014-12-51 was prompted by two incidents of crack propagation through the junction frame that initiated in the lower right-hand side between the web and the flange where the lower spar of the tailboom is joined. The cracks were significant in length and not visible from the outside of the helicopter. The NPRM was prompted by AD No. 2015-0033-E dated February 24, 2015 (AD 2015-0033-E), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition on Airbus Helicopters EC130B4 and EC130T2 helicopters. The NPRM proposed to require retaining the dye penetrant and borescope inspections in AD 2014-12-51 but with revised compliance times. The NRPM also proposed to change the applicability to helicopters with 690 hours TIS accumulated on the junction frame instead of on the helicopter, and proposed including an inspection interval defined in sling cycles. These actions were intended to detect a crack and to prevent failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter. Comments After our NPRM (80 FR 57742, September 25, 2015) was published, we received a comment from one commenter. Request One commenter requested the addition of a 10-hour or 250-sling cycle visual pilot check for helicopters with Modification 350A087421 or that have complied with Airbus Helicopters Service Bulletin No. EC130-53-029, Revision 0, dated February 20, 2015 (SB EC130-53-029). The commenter stated this pilot check would benefit operators and provide the same level of safety. We disagree. While the EASA AD allows the check requested by the commenter as an alternative method, because the cause of the fatigue cracking is still under investigation, we cannot determine that this method would correct the unsafe condition. FAA's Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA, reviewed the relevant information, considered the comment received, and determined the unsafe condition exists and is likely to exist or develop on other helicopters of the same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Differences Between This AD and the EASA AD The EASA AD includes alternate compliance instructions for helicopters modified with a cut-out in production by Airbus Helicopters Modification 350A087421 or in service by compliance with SB EC130-53- 029. This AD does not. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. 05A017, Revision 2, dated February 20, 2015 (EASB 05A017), for Model EC130B4 and EC130T2 helicopters. EASB 05A017 describes alternate procedures for inspecting outside the tailboom for a crack at reduced inspection intervals in combination with the internal inspections at extended intervals. EASB 05A017 also specifies adding sling cycles to the existing flight hour inspection interval for helicopters that perform external load-carrying operations. EASA issued AD No. 2015- 0033-E mandating the requirements in EASB 05A017 to ensure the continued airworthiness of these helicopters. This service information is reasonably available because the interested parties have access to it through their normal [[Page 26105]] course of business or by the means identified in the ADDRESSES section. Other Related Service Information Airbus Helicopters also issued SB EC130-53-029, which contains procedures to cut out the skin and splice at the junction frame to facilitate the external inspection specified in EASB 05A017. Costs of Compliance We estimate that this AD affects 208 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per work-hour, dye-penetrant inspecting the junction frame will require 1 work-hour, for a cost of $85 per helicopter and a total cost of $17,680 for the U.S. fleet, per inspection cycle. Borescope inspecting the junction frame will require 0.5 work-hour, for a cost of $43 per helicopter and a total cost of $8,944 for the U.S. fleet, per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on helicopters identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866; (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2014-12-51, Amendment 39-17921 (79 FR 45335, August 5, 2014), and adding the following new AD: 2016-08-20 Airbus Helicopters (Previously Eurocopter France): Amendment 39-18497; Docket No. FAA-2015-3970; Directorate Identifier 2015-SW-006-AD. (a) Applicability This AD applies to Airbus Helicopters Model EC130B4 and EC130T2 helicopters with a tailboom to fenestron junction frame (junction frame) that has 690 or more hours time-in-service (TIS), certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in the junction frame. This condition could result in failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2014-12-51, Amendment 39-17921 (79 FR 45335, August 5, 2014). (d) Effective Date This AD becomes effective June 6, 2016. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Before the junction frame reaches 700 hours TIS or within 10 hours TIS, whichever occurs later, remove the horizontal stabilizer, clean the junction frame, and dye-penetrant inspect around the circumference of the junction frame for a crack in the areas shown in Figure 1 of Airbus Helicopters EC130 Emergency Alert Service Bulletin No. 05A017, Revision 2, dated February 20, 2015 (EASB 05A017). Pay particular attention to the area around the 4 spars (item b) of Figure 1 of EASB 05A017. An example of a crack is shown in Figure 3 of EASB 05A017. (2) Within 25 hours TIS or 390 sling cycles, whichever occurs first after the inspection required by paragraph (f)(1) of this AD, and thereafter at intervals not exceeding 25 hours TIS or 390 sling cycles, whichever occurs first, either perform the actions of paragraph (f)(1) of this AD or, if the area is clean, using a borescope, inspect around the circumference of the junction frame for a crack in the areas shown in Figure 2 of EASB 05A017. Pay particular attention to the area around the 4 spars (item b) of Figure 2 of EASB 05A017. An example of a crack is shown in Figure 3 of EASB 05A017. For purposes of this AD, a sling cycle is defined as one landing with or without stopping the rotor or one external load- carrying operation; an external load-carrying operation occurs each time a helicopter picks up an external load and drops it off. (3) If there is a crack, before further flight, replace the junction frame. (g) Special Flight Permits Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222- 5110; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (i) Additional Information (1) Airbus Helicopters Service Bulletin No. EC130-53-029, Revision 0, dated February 20, 2015, which is not incorporated by reference, contains additional information about the subject of this final rule. For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. [[Page 26106]] (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015-0033-E, dated February 24, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-3970. (j) Subject Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tailboom. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Emergency Alert Service Bulletin No. 05A017, Revision 2, dated February 20, 2015. (ii) Reserved. (3) For Airbus Helicopters service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on April 15, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-09235 Filed 4-29-16; 8:45 am] BILLING CODE 4910-13-P
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for practices, methods, and procedures numbers 7003 through 7067 inclusive, 7069 (j) Related Information
the Administrator finds necessary for through 7990 inclusive, and 8000 through For more information about this AD,
safety in air commerce. This regulation 8999 inclusive. contact Cesar Gomez, Aerospace Engineer,
is within the scope of that authority (d) Subject Airframe and Mechanical Systems Branch,
because it addresses an unsafe condition ANE–171, FAA, New York ACO, 1600
Air Transport Association (ATA) of
that is likely to exist or develop on Stewart Avenue, Suite 410, Westbury, NY
America Code 27, Flight Controls.
11590; telephone 516–228–7318; fax 516–
products identified in this rulemaking
(e) Reason 794–5531.
action.
This AD was prompted by the discovery of (k) Material Incorporated by Reference
Regulatory Findings a number of incorrectly calibrated angle of
attack (AOA) transducers installed in the (1) The Director of the Federal Register
This AD will not have federalism stall protection system. We are issuing this approved the incorporation by reference
implications under Executive Order AD to detect and replace incorrectly (IBR) of the service information listed in this
13132. This AD will not have a calibrated AOA transducers; incorrect paragraph under 5 U.S.C. 552(a) and 1 CFR
substantial direct effect on the States, on calibration of the transducers could result in part 51.
the relationship between the national late activation of the stick pusher. (2) You must use this service information
government and the States, or on the as applicable to do the actions required by
(f) Compliance this AD, unless the AD specifies otherwise.
distribution of power and (i) Bombardier Service Bulletin 601R–27–
Comply with this AD within the
responsibilities among the various compliance times specified, unless already 164, dated March 30, 2015.
levels of government. done. (ii) Reserved.
For the reasons discussed above, I (3) For service information identified in
certify that this AD: (g) Replacement this AD, contact Bombardier, Inc., 400 Côte-
(1) Is not a ‘‘significant regulatory For AOA transducers identified in Vertu Road West, Dorval, Québec H4S 1Y9,
action’’ under Executive Order 12866, paragraph 1.A., ‘‘Effectivity,’’ of Bombardier Canada; telephone 514–855–5000; fax 514–
(2) Is not a ‘‘significant rule’’ under Service Bulletin 601R–27–164, dated March 855–7401; email
30, 2015: Within 2,500 flight hours or 12 thd.crj@aero.bombardier.com; Internet http://
DOT Regulatory Policies and Procedures months, whichever occurs first after the www.bombardier.com.
(44 FR 11034, February 26, 1979), effective date of this AD, replace the AOA (4) You may view this service information
(3) Will not affect intrastate aviation transducers with correctly calibrated AOA at FAA, Transport Airplane Directorate, 1601
in Alaska, and transducers, in accordance with the Lind Avenue SW., Renton, WA. For
(4) Will not have a significant Accomplishment Instructions of Bombardier information on the availability of this
economic impact, positive or negative, Service Bulletin 601R–27–164, dated March material at the FAA, call 425–227–1221.
on a substantial number of small entities 30, 2015. (5) You may view this service information
under the criteria of the Regulatory (h) Parts Installation Prohibition that is incorporated by reference at the
Flexibility Act. National Archives and Records
As of the effective date of this AD, no
Administration (NARA). For information on
List of Subjects in 14 CFR Part 39 person may install, on any airplane, an AOA
the availability of this material at NARA, call
transducer having a part number or serial
202–741–6030, or go to: http://
Air transportation, Aircraft, Aviation number listed in paragraph 1.A.,
‘‘Effectivity,’’ of Bombardier Service Bulletin www.archives.gov/federal-register/cfr/ibr-
safety, Incorporation by reference, locations.html.
Safety. 601R–27–164, dated March 30, 2015.
Issued in Renton, Washington, on April 20,
Adoption of the Amendment (i) Other FAA AD Provisions
2016.
The following provisions also apply to this John P. Piccola, Jr.,
Accordingly, under the authority AD:
delegated to me by the Administrator, (1) Alternative Methods of Compliance Acting Manager, Transport Airplane
the FAA amends 14 CFR part 39 as (AMOCs): The Manager, New York Aircraft Directorate, Aircraft Certification Service.
follows: Certification Office (ACO), ANE–170, FAA, [FR Doc. 2016–09791 Filed 4–29–16; 8:45 am]
has the authority to approve AMOCs for this BILLING CODE 4910–13–P
PART 39—AIRWORTHINESS AD, if requested using the procedures found
DIRECTIVES in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal DEPARTMENT OF TRANSPORTATION
■ 1. The authority citation for part 39 inspector or local Flight Standards District
continues to read as follows: Office, as appropriate. If sending information
Federal Aviation Administration
directly to the ACO, send it to ATTN:
Authority: 49 U.S.C. 106(g), 40113, 44701. Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart 14 CFR Part 39
§ 39.13 [Amended] Avenue, Suite 410, Westbury, NY 11590; [Docket No. FAA–2015–3970; Directorate
■ 2. The FAA amends § 39.13 by adding telephone 516–228–7300; fax 516–794–5531. Identifier 2015–SW–006–AD; Amendment
the following new airworthiness Before using any approved AMOC, notify 39–18497; AD 2016–08–20]
your appropriate principal inspector, or
directive (AD): lacking a principal inspector, the manager of RIN 2120–AA64
2016–09–04 Bombardier, Inc.: Amendment the local flight standards district office/
39–18502; Docket No. FAA–2015–4814; certificate holding district office. The AMOC Airworthiness Directives; Airbus
Directorate Identifier 2015–NM–105–AD. approval letter must specifically reference Helicopters (Previously Eurocopter
this AD. France)
(a) Effective Date (2) Contacting the Manufacturer: For any
This AD is effective June 6, 2016. requirement in this AD to obtain corrective AGENCY: Federal Aviation
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actions from a manufacturer, the action must Administration (FAA), DOT.
(b) Affected ADs be accomplished using a method approved
None. by the Manager, New York ACO, ANE–170, ACTION: Final rule.
FAA; or Transport Canada Civil Aviation
(c) Applicability (TCCA); or Bombardier, Inc.’s TCCA Design SUMMARY: We are superseding
This AD applies to Bombardier, Inc. Model Approval Organization (DAO). If approved by airworthiness directive (AD) 2014–12–
CL–600–2B19 (Regional Jet Series 100 & 440) the DAO, the approval must include the 51 for Airbus Helicopters (previously
airplanes, certificated in any category, serial DAO-authorized signature. Eurocopter France) Model EC130B4 and
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course of business or by the means (3) Will not affect intrastate aviation (f) Required Actions
identified in the ADDRESSES section. in Alaska to the extent that it justifies (1) Before the junction frame reaches 700
making a regulatory distinction; and hours TIS or within 10 hours TIS, whichever
Other Related Service Information occurs later, remove the horizontal stabilizer,
(4) Will not have a significant clean the junction frame, and dye-penetrant
Airbus Helicopters also issued SB
economic impact, positive or negative, inspect around the circumference of the
EC130–53–029, which contains
on a substantial number of small entities junction frame for a crack in the areas shown
procedures to cut out the skin and
under the criteria of the Regulatory in Figure 1 of Airbus Helicopters EC130
splice at the junction frame to facilitate
Flexibility Act. Emergency Alert Service Bulletin No.
the external inspection specified in 05A017, Revision 2, dated February 20, 2015
EASB 05A017. We prepared an economic evaluation
(EASB 05A017). Pay particular attention to
of the estimated costs to comply with the area around the 4 spars (item b) of Figure
Costs of Compliance this AD and placed it in the AD docket. 1 of EASB 05A017. An example of a crack
We estimate that this AD affects 208 List of Subjects in 14 CFR Part 39 is shown in Figure 3 of EASB 05A017.
helicopters of U.S. Registry. We estimate (2) Within 25 hours TIS or 390 sling cycles,
that operators may incur the following Air transportation, Aircraft, Aviation whichever occurs first after the inspection
costs in order to comply with this AD. required by paragraph (f)(1) of this AD, and
safety, Incorporation by reference,
At an average labor rate of $85 per work- thereafter at intervals not exceeding 25 hours
Safety. TIS or 390 sling cycles, whichever occurs
hour, dye-penetrant inspecting the first, either perform the actions of paragraph
junction frame will require 1 work-hour, Adoption of the Amendment
(f)(1) of this AD or, if the area is clean, using
for a cost of $85 per helicopter and a Accordingly, under the authority a borescope, inspect around the
total cost of $17,680 for the U.S. fleet, delegated to me by the Administrator, circumference of the junction frame for a
per inspection cycle. Borescope the FAA amends 14 CFR part 39 as crack in the areas shown in Figure 2 of EASB
inspecting the junction frame will 05A017. Pay particular attention to the area
follows: around the 4 spars (item b) of Figure 2 of
require 0.5 work-hour, for a cost of $43
per helicopter and a total cost of $8,944 EASB 05A017. An example of a crack is
PART 39—AIRWORTHINESS shown in Figure 3 of EASB 05A017. For
for the U.S. fleet, per inspection cycle. DIRECTIVES purposes of this AD, a sling cycle is defined
Authority for This Rulemaking as one landing with or without stopping the
■ 1. The authority citation for part 39 rotor or one external load-carrying operation;
Title 49 of the United States Code an external load-carrying operation occurs
continues to read as follows:
specifies the FAA’s authority to issue each time a helicopter picks up an external
rules on aviation safety. Subtitle I, Authority: 49 U.S.C. 106(g), 40113, 44701. load and drops it off.
section 106, describes the authority of § 39.13 [Amended] (3) If there is a crack, before further flight,
the FAA Administrator. Subtitle VII: replace the junction frame.
Aviation Programs, describes in more ■ 2. The FAA amends § 39.13 by (g) Special Flight Permits
detail the scope of the Agency’s removing Airworthiness Directive (AD) Special flight permits are prohibited.
authority. 2014–12–51, Amendment 39–17921 (79
We are issuing this rulemaking under FR 45335, August 5, 2014), and adding (h) Alternative Methods of Compliance
the authority described in Subtitle VII, the following new AD: (AMOCs)
Part A, Subpart III, Section 44701: (1) The Manager, Safety Management
2016–08–20 Airbus Helicopters (Previously
‘‘General requirements.’’ Under that Eurocopter France): Amendment 39– Group, FAA, may approve AMOCs for this
section, Congress charges the FAA with AD. Send your proposal to: Robert Grant,
18497; Docket No. FAA–2015–3970;
promoting safe flight of civil aircraft in Aviation Safety Engineer, Safety Management
Directorate Identifier 2015–SW–006–AD.
air commerce by prescribing regulations Group, Rotorcraft Directorate, FAA, 10101
(a) Applicability Hillwood Pkwy., Fort Worth, TX 76177;
for practices, methods, and procedures
This AD applies to Airbus Helicopters telephone (817) 222–5110; email 9-ASW-
the Administrator finds necessary for FTW-AMOC-Requests@faa.gov.
safety in air commerce. This regulation Model EC130B4 and EC130T2 helicopters
with a tailboom to fenestron junction frame (2) For operations conducted under a 14
is within the scope of that authority CFR part 119 operating certificate or under
(junction frame) that has 690 or more hours
because it addresses an unsafe condition time-in-service (TIS), certificated in any 14 CFR part 91, subpart K, we suggest that
that is likely to exist or develop on category. you notify your principal inspector, or
helicopters identified in this rulemaking lacking a principal inspector, the manager of
action. (b) Unsafe Condition the local flight standards district office or
This AD defines the unsafe condition as a certificate holding district office, before
Regulatory Findings crack in the junction frame. This condition operating any aircraft complying with this
This AD will not have federalism could result in failure of the junction frame, AD through an AMOC.
implications under Executive Order which could result in loss of the Fenestron (i) Additional Information
13132. This AD will not have a and subsequent loss of control of the
helicopter. (1) Airbus Helicopters Service Bulletin No.
substantial direct effect on the States, on EC130–53–029, Revision 0, dated February
the relationship between the national (c) Affected ADs 20, 2015, which is not incorporated by
government and the States, or on the This AD supersedes AD 2014–12–51, reference, contains additional information
distribution of power and Amendment 39–17921 (79 FR 45335, August about the subject of this final rule. For
responsibilities among the various 5, 2014). service information identified in this final
levels of government. rule, contact Airbus Helicopters, Inc., 2701
(d) Effective Date
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N. Forum Drive, Grand Prairie, TX 75052;
For the reasons discussed above, I
This AD becomes effective June 6, 2016. telephone (972) 641–0000 or (800) 232–0323;
certify that this AD: fax (972) 641–3775; or at http://
(1) Is not a ‘‘significant regulatory (e) Compliance www.airbushelicopters.com/techpub. You
action’’ under Executive Order 12866; You are responsible for performing each may review a copy of the service information
(2) Is not a ‘‘significant rule’’ under action required by this AD within the at the FAA, Office of the Regional Counsel,
DOT Regulatory Policies and Procedures specified compliance time unless it has Southwest Region, 10101 Hillwood Pkwy.,
(44 FR 11034, February 26, 1979); already been accomplished prior to that time. Room 6N–321, Fort Worth, TX 76177.
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(2) The subject of this AD is addressed in Piper Aircraft, Inc. Model PA–31–350 airplanes. The SNPRM published in the
European Aviation Safety Agency (EASA) AD airplanes. This AD was prompted by a Federal Register on January 26, 2016
No. 2015–0033–E, dated February 24, 2015. report of an engine fire caused by a leak (81 FR 4214). We preceded the SNPRM
You may view the EASA AD on the Internet in the fuel pump inlet hose. This AD with a notice of proposed rulemaking
at http://www.regulations.gov in Docket No.
FAA–2015–3970.
requires inspecting the fuel hose (NPRM) that published in the Federal
assembly and the turbocharger support Register on June 3, 2014 (79 FR 31888).
(j) Subject assembly for proper clearance between The NPRM proposed to require
Joint Aircraft Service Component (JASC) them, inspecting each assembly for any inspecting the fuel hose assembly and
Code: 5302: Rotorcraft Tailboom. sign of damage, and making any the turbocharger support assembly for
(k) Material Incorporated by Reference necessary repairs or replacements. We proper clearance between them,
are issuing this AD to correct the unsafe inspecting each assembly for any sign of
(1) The Director of the Federal Register
approved the incorporation by reference of
condition on these products. damage, and making any necessary
the service information listed in this DATES: This AD is effective June 6, 2016. repairs or replacements. The NPRM was
paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register prompted by a report of an engine fire
part 51. approved the incorporation by reference on a Piper Aircraft, Inc. (Piper) Model
(2) You must use this service information of a certain publication listed in this AD PA–31–350 airplane. Investigation
as applicable to do the actions required by as of June 6, 2016. revealed that the fire was caused by a
this AD, unless the AD specifies otherwise. leak in the fuel pump inlet hose that
ADDRESSES: For service information
(i) Airbus Helicopters Emergency Alert resulted from repeated contact with an
Service Bulletin No. 05A017, Revision 2, identified in this final rule, contact
Piper Aircraft, Inc., 2926 Piper Drive, adjacent turbocharger support assembly
dated February 20, 2015.
(ii) Reserved. Vero Beach, Florida 32960; telephone: caused by inadequate clearance between
(3) For Airbus Helicopters service (772) 567–4361; fax: (772) 978–6573; the two assemblies. The SNPRM
information identified in this final rule, Internet: www.piper.com/home/pages/ proposed to require the same actions as
contact Airbus Helicopters, Inc., 2701 N. Publications.cfm. You may view this proposed in the NPRM using revised
Forum Drive, Grand Prairie, TX 75052; referenced service information at the service information issued by the
telephone (972) 641–0000 or (800) 232–0323; FAA, Small Airplane Directorate, 901 manufacturer to clarify which engines
fax (972) 641–3775; or at http:// are part of the airplane applicability and
Locust, Kansas City, Missouri 64106.
www.airbushelicopters.com/techpub. to revise the instructions for
(4) You may view this service information For information on the availability of
this material at the FAA, call (816) 329– accomplishing the proposed actions.
at FAA, Office of the Regional Counsel,
4148. It is also available on the internet This condition, if not corrected, could
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For at http://www.regulations.gov by result in damage to the fuel inlet hose
information on the availability of this searching for and locating Docket No. assembly, which could cause the fuel
material at the FAA, call (817) 222–5110. FAA–2014–0338. pump inlet hose to fail and leak fuel in
(5) You may view this service information the engine compartment. This condition
that is incorporated by reference at the Examining the AD Docket could also cause damage to the
National Archives and Records You may examine the AD docket on turbocharger support assembly, which
Administration (NARA). For information on the Internet at http:// could require the turbocharger support
the availability of this material at NARA, call assembly to be repaired or replaced.
(202) 741–6030, or go to: http://
www.regulations.gov by searching for
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2014– Comments
locations.html. 0338; or in person at the Docket
Management Facility between 9 a.m. We gave the public the opportunity to
Issued in Fort Worth, Texas, on April 15, participate in developing this AD. We
2016.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket received no comments on the SNPRM
Scott A. Horn, (81 FR 4214, January 26, 2016) or on the
contains this AD, the regulatory
Acting Manager, Rotorcraft Directorate, evaluation, any comments received, and determination of the cost to the public.
Aircraft Certification Service.
other information. The address for the Conclusion
[FR Doc. 2016–09235 Filed 4–29–16; 8:45 am]
Docket Office (phone: 800–647–5527) is
BILLING CODE 4910–13–P We reviewed the relevant data and
Document Management Facility, U.S.
determined that air safety and the
Department of Transportation, Docket
public interest require adopting this AD
Operations, M–30, West Building
DEPARTMENT OF TRANSPORTATION as proposed except for minor editorial
Ground Floor, Room W12–140, 1200
changes. We have determined that these
Federal Aviation Administration New Jersey Avenue SE., Washington,
minor changes:
DC 20590. • Are consistent with the intent that
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Gary was proposed in the SNPRM (81 FR
Wechsler, Aerospace Engineer, FAA, 4214, January 26, 2016) for correcting
[Docket No. FAA–2014–0338; Directorate Atlanta Aircraft Certification Office,
Identifier 2014–CE–010–AD; Amendment the unsafe condition; and
39–18495; AD 2016–08–18]
1701 Columbia Avenue, College Park, • Do not add any additional burden
Georgia 30337; telephone: (404) 474– upon the public than was already
RIN 2120–AA64 5575; fax: (404) 474–5606; email: proposed in the SNPRM (81 FR 4214,
gary.wechsler@faa.gov. January 26, 2016).
Airworthiness Directives; Piper SUPPLEMENTARY INFORMATION:
mstockstill on DSK3G9T082PROD with RULES
Aircraft, Inc. Airplanes Related Service Information Under 1
Discussion CFR Part 51
AGENCY: Federal Aviation
Administration (FAA), DOT. We issued a supplemental notice of We reviewed Piper Aircraft, Inc.
ACTION: Final rule. proposed rulemaking (SNPRM) to Service Bulletin No. 1257A, dated
amend 14 CFR part 39 by adding an AD August 4, 2015. The service information
SUMMARY: We are adopting a new that would apply to certain Piper describes procedures for the following.
airworthiness directive (AD) for certain Aircraft, Inc. Model PA–31–350 This service information is reasonably
VerDate Sep<11>2014 17:39 Apr 29, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\02MYR1.SGM 02MYR1](https://thefederalregister.org/doc/81_FR_26187/page/4.svg)
Document Created: 2016-04-30 13:34:48
Document Modified: 2016-04-30 13:34:48
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective June 6, 2016. | |
| Contact | Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; email [email protected] | |
| FR Citation | 81 FR 26103 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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